An on-board intelligent warming control system

Abstract

The application provides an airborne intelligent heating control system, and belongs to the technical field of airborne sensor / inductor heating control. Specifically, a heating control box receives wheel load state, indicated airspeed, atmospheric total temperature and other information sent by an airborne probe atmospheric data computer, and a forced heating signal of an on-board top control panel, and judges accordingly. The first heating control box and the second heating control box jointly realize heating control of each component of the atmospheric data system, monitor the heating state of each component in real time, and send the heating state information of each component to the airborne probe atmospheric data computer. On the basis of time-sharing starting, in order to avoid the heating power acting on the same load at the same time, rigorous theoretical proof is carried out, various fault conditions are considered, the two heating control boxes on the aircraft are reasonably and efficiently used, the double-redundancy advantage is exerted, and the safety of the aircraft is ensured.

Description

Technical Field

[0001] This application relates to the field of airborne sensor / receiver heating control, and in particular to an airborne intelligent heating control system. Background Technology

[0002] Currently, all onboard heating control systems are implemented purely in hardware, without the introduction of software for intelligent control. This causes a problem: the dual-redundant heating design on the aircraft essentially involves designing different heating power supplies. If these power supplies are simply applied to the airborne probes simultaneously, it is equivalent to applying two power supplies to a single load. If one power supply is of poor quality, it can easily lead to one power supply supplying power to the other or one power supply being damaged, which is extremely dangerous.

[0003] Furthermore, without intelligent software control, precise monitoring and detection of heating cannot be achieved, leading to unresolved issues related to the application and voting of redundant information in the redundant intelligent probe-type atmospheric data computer. Inability to effectively utilize redundant voting data can also cause heating malfunctions in the aircraft's sensor systems. Summary of the Invention

[0004] In view of this, this application provides an airborne intelligent heating control system, which solves the problems in the prior art and improves the stability of airborne heating system operation.

[0005] The airborne intelligent heating control system provided in this application adopts the following technical solution:

[0006] An airborne intelligent heating control system includes a first heating control box and a second heating control box. The first heating control box is communicatively connected to an airborne probe-type atmospheric data computer and various components of the onboard atmospheric data system. The second heating control box is communicatively connected to an airborne probe-type atmospheric data computer and various components of the onboard atmospheric data system.

[0007] After the system is powered on, the first heating control box acts as the main heating control box, and the second heating control box acts as the backup heating control box.

[0008] The main heating control box receives aircraft flight data and environmental data sent by the probe-type air data computer. Based on the aircraft flight data and environmental data, the main heating control box decides whether to start heating of each component of the air data system.

[0009] When the main heating control box detects heating failures in various components of the air data system during heating status detection, the airborne probe-type air data computer sends the heating failure information, aircraft flight data, and environmental data to the backup heating control box. The backup heating control box then reheats the components of the air data system that have failed to heat up.

[0010] Optionally, if there is a communication failure between the airborne probe-type atmospheric data computer and the first heating control box, the second heating control box shall serve as the main heating control box and the first heating control box shall serve as the backup heating control box.

[0011] Optionally, the main heating control box determines whether to start heating of each component of the air data system based on the aircraft flight data and environmental data. The main heating control box then determines the heating mode of each component of the air data system based on the received aircraft flight data and environmental data. The heating modes include full heating and half heating.

[0012] When the main heating control box detects heating failures in various components of the atmospheric data system during heating status detection, the backup heating control box reheats the failed components of the atmospheric data system according to the heating mode determined by the main heating control box.

[0013] Optionally, the airborne probe-type atmospheric data computer is provided with four units, and the first heating control box and the four airborne probe-type atmospheric data computers are all communicatively connected, as are the second heating control box and the four airborne probe-type atmospheric data computers.

[0014] When the information provided by all four airborne probe-type atmospheric data computers is valid:

[0015] If the information provided by the four airborne probe-type atmospheric data computers to the main heating control box is consistent, the main heating control box determines whether to heat each component of the atmospheric data system and determines the heating mode according to the received information.

[0016] If the information provided by the four airborne probe-type atmospheric data computers to the main heating control box is inconsistent, the main heating control box will select the information with the highest priority in the order of full heating, half heating, and no heating to determine whether to heat each component of the atmospheric data system and the heating mode.

[0017] Optionally, when the information provided by one or more airborne probe-type atmospheric data computers is invalid or there is a communication interruption, the main heating control box uses valid data from other airborne probe-type atmospheric data computers to make a judgment and control the heating of each component of the atmospheric data system.

[0018] Optionally, if the information provided by the four airborne probe-type atmospheric data computers is invalid, the main heating control box will not use the data from this time, and the main heating control box will receive an information fault mode signal.

[0019] Optionally, both the first and second heating control boxes communicate with the airborne probe-type atmospheric data computer via an RS-422A bus.

[0020] In summary, this application includes the following beneficial technical effects:

[0021] This application's heating control box receives information such as wheel load status, indicated airspeed, and total atmospheric temperature from the airborne probe-type air data computer, as well as forced heating signals from the aircraft's top control panel. Based on this information, it makes judgments. The first and second heating control boxes jointly control the heating of various components of the air data system, monitor the heating status of each component in real time, and send the heating status information of each component to the airborne probe-type air data computer. Based on time-sharing startup, this application conducts rigorous reasoning and argumentation to avoid simultaneous application of heating power to the same load, considering various fault scenarios, to ensure the rational and efficient cooperation of the two onboard heating control boxes, leveraging the advantages of dual redundancy and ensuring aircraft safety. Attached Figure Description

[0022] To more clearly illustrate the technical solutions of the embodiments of this application, the drawings used in the embodiments will be briefly introduced below. Obviously, the drawings described below are only some embodiments of this application. For those skilled in the art, other drawings can be obtained based on these drawings without creative effort.

[0023] Figure 1 This is a schematic diagram of the airborne intelligent heating control system according to an embodiment of this application. Detailed Implementation

[0024] The embodiments of this application will now be described in detail with reference to the accompanying drawings.

[0025] The following specific examples illustrate the implementation of this application. Those skilled in the art can easily understand other advantages and effects of this application from the content disclosed in this specification. Obviously, the described embodiments are only a part of the embodiments of this application, and not all of them. This application can also be implemented or applied through other different specific embodiments, and the details in this specification can also be modified or changed based on different viewpoints and applications without departing from the spirit of this application. It should be noted that, in the absence of conflict, the following embodiments and features in the embodiments can be combined with each other. Based on the embodiments in this application, all other embodiments obtained by those skilled in the art without creative effort are within the scope of protection of this application.

[0026] It should be noted that various aspects of embodiments within the scope of the appended claims are described below. It will be apparent that the aspects described herein can be embodied in a wide variety of forms, and any particular structure and / or function described herein is merely illustrative. Based on this application, those skilled in the art will understand that one aspect described herein can be implemented independently of any other aspect, and two or more of these aspects can be combined in various ways. For example, any number of aspects set forth herein can be used to implement the device and / or practice the method. Additionally, this device and / or method can be implemented using structures and / or functionalities other than one or more of the aspects set forth herein.

[0027] It should also be noted that the illustrations provided in the following embodiments are only schematic representations of the basic concept of this application. The drawings only show the components related to this application and are not drawn according to the actual number, shape and size of the components in the actual implementation. In the actual implementation, the form, quantity and proportion of each component can be arbitrarily changed, and the layout of the components may also be more complex.

[0028] Furthermore, specific details are provided in the following description to facilitate a thorough understanding of the examples. However, those skilled in the art will understand that the described aspects can be practiced without these specific details.

[0029] This application provides an airborne intelligent heating control system.

[0030] like Figure 1 As shown, an airborne intelligent heating control system includes a first heating control box and a second heating control box. The first heating control box is communicatively connected to the airborne probe-type atmospheric data computer and various components of the onboard atmospheric data system, and the second heating control box is communicatively connected to the airborne probe-type atmospheric data computer and various components of the onboard atmospheric data system.

[0031] After the system is powered on, the first heating control box acts as the main heating control box, and the second heating control box acts as the backup heating control box.

[0032] The main heating control box receives aircraft flight data and environmental data sent by the probe-type atmospheric data computer. Based on the aircraft flight data and environmental data, the main heating control box decides whether to start heating of each component of the atmospheric data system.

[0033] When the main heating control box detects heating failures in various components of the air data system during heating status detection, the airborne probe-type air data computer sends the heating failure information, aircraft flight data, and environmental data to the backup heating control box. The backup heating control box then reheats the components of the air data system that have failed to heat up.

[0034] The heating control box identifies the main heating control box and the backup heating control box based on the installation location information. After the system is powered on, the first heating control box mainly completes the system heating. If the heating of the entire system or a certain component fails, the second heating control box controls the system or component to perform supplementary heating.

[0035] If there is a communication failure between the airborne probe-type atmospheric data computer and the first heating control box, the second heating control box will act as the main heating control box, and the first heating control box will act as the backup heating control box.

[0036] The atmospheric data system disclosed in this application includes four fuselage pressure sensors, four angle-of-attack sensors, and two total temperature sensors.

[0037] This application's heating control system comprises two redundant and interchangeable heating control boxes, with one system configured for the entire aircraft. The heating control boxes are interconnected with an airborne probe-type atmospheric data computer, four fuselage pressure sensors, four angle-of-attack sensors, and two total temperature sensors. The heating control boxes receive flight data and environmental data from the airborne probe-type atmospheric data computer, and make judgments accordingly. The first and second heating control boxes jointly control the heating of each component of the atmospheric data system, monitor the heating status of each component in real time, and send the heating status information of each component back to the airborne probe-type atmospheric data computer. The flight data and environmental data include wheel load status, indicated airspeed, total atmospheric temperature, and forced heating signals from the aircraft's top control panel.

[0038] Based on time-sharing start-up, this application has conducted rigorous reasoning and demonstration to avoid the heating power supply acting on the same load at the same time. It takes into account various fault scenarios to enable the two heating control boxes on the aircraft to work together in a reasonable and efficient manner, giving full play to the advantages of dual redundancy and ensuring aircraft safety.

[0039] The main heating control box determines whether to start heating of the components of the air data system based on the aircraft flight data and environmental data. The heating modes include full heating and half heating.

[0040] When the main heating control box detects heating failures in various components of the atmospheric data system during heating status detection, the backup heating control box reheats the failed components of the atmospheric data system according to the heating mode determined by the main heating control box.

[0041] The airborne probe-type atmospheric data computer is provided with four units. The first heating control box and the four airborne probe-type atmospheric data computers are all communicatively connected, as are the second heating control box and the four airborne probe-type atmospheric data computers. All of the airborne probe-type atmospheric data computers are intelligent probe-type atmospheric data computers.

[0042] When the information provided by all four airborne probe-type atmospheric data computers is valid:

[0043] If the information provided by the four airborne probe-type air data computers to the main heating control box is consistent, the main heating control box determines whether to heat the components of the air data system and determines the heating mode based on the received information; if the information provided by the four airborne probe-type air data computers to the main heating control box is inconsistent, the main heating control box selects the information with the highest priority in the order of full heating, half heating, and no heating to determine whether to heat the components of the air data system and the heating mode.

[0044] When the information provided by one or more airborne probe-type atmospheric data computers is invalid or there is a communication interruption, the main heating control box uses valid data from other airborne probe-type atmospheric data computers to make a judgment and control the heating of each component of the atmospheric data system.

[0045] When the information provided by the four airborne probe-type atmospheric data computers is invalid, the main heating control box will not use the data from this time, and the main heating control box will receive an information fault mode signal.

[0046] This application features an innovative configuration that physically links the device to four onboard air data computers and four fuselage pressure sensors, creating a natural cross-linking advantage. When the heating information received from the four onboard probe-type air data computers is inconsistent, a predetermined logic is used to filter and make a decision.

[0047] During the initialization phase of the aircraft's electric heating control system, each heating control box in the heating control system will perform an initial pressure consistency test. The consistency test includes: intelligent probe-type atmospheric data computer, fuselage pressure sensor, and angle of attack sensor.

[0048] If the initial pressures transmitted by the four intelligent probe-type atmospheric data computers are consistent, it indicates that the atmospheric data system is fault-free. If the initial pressures transmitted by the four intelligent probe-type atmospheric data computers are inconsistent, and one of them is inconsistent with the other three, it is considered that the pressure acquisition of the corresponding channel is faulty, and a pressure detection fault for that channel is reported. If two of them are consistent, a pressure consistency detection fault is reported.

[0049] The heating power supply for the intelligent probe-type atmospheric data computer, angle of attack sensor, and total temperature sensor in the system is 115VAC / 400HZ. Considering the limitation of the maximum power of 115VAC / 400HZ on the aircraft (the instantaneous maximum power is less than 4000VA), the heating control box software needs to start the 115VAC heating components in groups and at different times.

[0050] The heating power supply for the body pressure sensor is 28VDC, and its heating does not require a delay start.

[0051] The time-sharing group-based start-up system for heating is only applicable when the aircraft is on the ground. When the heating system is started for the first time, after the aircraft has completed ground checks, taxied, and entered flight, the system has already completed the heating start-up and entered rated power operation.

[0052] The heating control box software activates the intelligent probe-type atmospheric data computer, angle-of-attack sensor, and total temperature sensor in five groups by setting the status information of the DSP's GPIO ports. Each group of components is activated after a 30-second delay before activating the next group.

[0053] This invention reverse-engineers the heating current in the heating circuit based on the collected heating current output voltage (voltage acquisition formula V=2.5±X*IP), and applies the formula P=U*I to obtain the power of each airborne sensor / receiver, and sums them up to obtain the power, providing a reference for the heating power of the onboard atmospheric data system.

[0054] Both the first and second heating control boxes communicate with the airborne probe-type atmospheric data computer via an RS-422A bus.

[0055] The above description is merely a specific embodiment of this application, but the scope of protection of this application is not limited thereto. Any variations or substitutions that can be easily conceived by those skilled in the art within the technical scope disclosed in this application should be included within the scope of protection of this application. Therefore, the scope of protection of this application should be determined by the scope of the claims.

Claims

1. An airborne intelligent heating control system, characterized in that, It includes a first heating control box and a second heating control box. The first heating control box is communicatively connected to the airborne probe-type air data computer and various components of the air data system on the aircraft. The second heating control box is communicatively connected to the airborne probe-type air data computer and various components of the air data system on the aircraft. After the system is powered on, the first heating control box acts as the main heating control box, and the second heating control box acts as the backup heating control box. The main heating control box receives aircraft flight data and environmental data sent by the probe-type air data computer. Based on the aircraft flight data and environmental data, the main heating control box decides whether to start heating of each component of the air data system. When the main heating control box detects heating failures in various components of the air data system during heating status detection, the airborne probe-type air data computer sends the heating failure information, aircraft flight data, and environmental data to the backup heating control box, which then reheats the components of the air data system that have failed to heat up. If there is a communication failure between the airborne probe-type atmospheric data computer and the first heating control box, the second heating control box will act as the main heating control box and the first heating control box will act as the backup heating control box. The main heating control box determines whether to start heating of each component of the air data system based on the aircraft flight data and environmental data. The main heating control box then determines the heating mode of each component of the air data system based on the received aircraft flight data and environmental data. The heating modes include full heating and half heating. When the main heating control box detects heating failures in various components of the atmospheric data system during heating status detection, the backup heating control box reheats the failed components of the atmospheric data system according to the heating mode determined by the main heating control box. The airborne probe-type atmospheric data computer is provided with four units. The first heating control box and the four airborne probe-type atmospheric data computers are all connected in communication. The second heating control box and the four airborne probe-type atmospheric data computers are also connected in communication. When the information provided by all four airborne probe-type atmospheric data computers is valid: If the information provided by the four airborne probe-type atmospheric data computers to the main heating control box is consistent, the main heating control box determines whether to heat each component of the atmospheric data system and determines the heating mode according to the received information. If the information provided by the four airborne probe-type atmospheric data computers to the main heating control box is inconsistent, the main heating control box will select the information with the highest priority in the order of full heating, half heating, and no heating to determine whether to heat each component of the atmospheric data system and the heating mode.

2. The airborne intelligent heating control system according to claim 1, characterized in that, When the information provided by one or more airborne probe-type atmospheric data computers is invalid or there is a communication interruption, the main heating control box uses valid data from other airborne probe-type atmospheric data computers to make a judgment and control the heating of each component of the atmospheric data system.

3. The airborne intelligent heating control system according to claim 2, characterized in that, When the information provided by the four airborne probe-type atmospheric data computers is invalid, the main heating control box will not use the data from this time, and the main heating control box will receive an information fault mode signal.

4. The airborne intelligent heating control system according to claim 1, characterized in that, Both the first and second heating control boxes communicate with the airborne probe-type atmospheric data computer via an RS-422A bus.

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